FIELD
[0001] The present disclosure relates to aerodynamic structures, and more specifically,
to improved aerodynamic properties of aerodynamic structures using air flow control.
BACKGROUND
[0002] The performance of aerodynamic structures depends primarily on the lift and drag
forces created at the surface of the structures in response to passing air flow. Mechanically
fixed surfaces may be selectively included at aerodynamic surfaces, such as rotor
blades, wings, engine inlets, fan blades, nozzles, etc., in order to alter local aerodynamic
properties and thus achieve desired aerodynamic properties for those aerodynamic structures.
Additionally, movable control surfaces, such as flaps, slats, spoilers, ailerons,
elevators, and rudders, may be included in or on the aerodynamic surfaces in order
to dynamically alter the geometry of the aerodynamic surface, thus altering the aerodynamic
properties of the structure.
[0003] Beyond the various mechanical means included on aerodynamic structures, aerodynamic
properties of the structures may also be altered by causing effects on the passing
air flow. These effects may be generated by various actuating devices disposed in
or on the aerodynamic surface or device.
SUMMARY
[0004] One embodiment provides a synthetic jet actuator that includes an aerodynamic structure
having an aerodynamic surface and forming an aperture through the aerodynamic surface.
The synthetic jet actuator also includes one or more walls forming a chamber within
the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber
is in fluid communication with an ambient environment through the aperture. The synthetic
jet actuator also includes an ionizing device disposed at the aperture and configured
to ionize chamber gases exiting through the aperture.
[0005] Another embodiment provides an aircraft that includes a thrust source and one or
more lifting surfaces configured to generate a lift force when coupled to the thrust
source. The aircraft also includes at least one synthetic jet actuator configured
to provide air flow control at an aerodynamic surface of the aircraft, the aerodynamic
structure having an aerodynamic surface and forming an aperture through the aerodynamic
surface. The synthetic jet actuator includes one or more walls forming a chamber within
the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber
is in fluid communication with an ambient environment through the aperture. The synthetic
jet actuator also includes an ionizing device disposed at the aperture and configured
to ionize chamber gases exiting through the aperture.
[0006] Another embodiment provides a method for flying an aircraft that includes using a
thrust source to generate a lift force at one or more lifting surfaces of the aircraft,
and providing air flow control at an aerodynamic structure of the aircraft by ionizing
one or more gases exiting from a synthetic jet actuator disposed in the aerodynamic
structure.
[0007] A plasma-assisted synthetic jet device, an aircraft including a plasma-assisted synthetic
jet device, and a method of improving aerodynamic properties are disclosed for providing
air flow control at an aerodynamic structure by ionizing one or more gases exiting
through an aperture of the synthetic jet device disposed in the aerodynamic structure.
[0008] The invention can involve a plasma-assisted synthetic jet actuator that may include
an aerodynamic structure having an aerodynamic surface and forming an aperture through
the aerodynamic surface; one or more walls forming a chamber within the aerodynamic
structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid
communication with an ambient environment through the aperture; and an ionizing device
disposed at the aperture and configured to ionize one or more chamber gases exiting
through the aperture. A pressure differential between the chamber and the ambient
environment may cause the one or more chamber gases to exit through the aperture.
The plasma-assisted synthetic jet actuator may also include a gas propulsion device
configured to propel the one or more chamber gases through the aperture. The gas propulsion
device may be a piezoelectric-actuated diaphragm. The ionizing device and the gas
propulsion device may be the same device. The ionizing device may include first and
second electrodes disposed on opposing sides of the aerodynamic surface. The plasma-assisted
synthetic jet actuator may further comprise an insulating layer configured to at least
partially cover one of the first and second electrodes. The ionized chamber gases
may be steerable using at least one of an actuating device configured to pivot the
plasma-assisted synthetic jet actuator and one or more electromagnets adjacent to
the plasma-assisted synthetic jet actuator. The plasma-assisted synthetic jet actuator
may also include a first power supply providing a first signal to the gas propulsion
device, and a second power supply providing a second signal to the ionizing device,
wherein the first signal is synchronized with the second signal. A pulse of the second
signal may be delayed by a predetermined amount from a pulse of the first signal,
the predetermined amount based on an amount of time for a volume of the propelled
one or more chamber gases to reach the aperture.
[0009] The invention can involve an aircraft that may include a thrust source; one or more
lifting surfaces configured to generate a lift force when coupled to the thrust source;
and at least one plasma-assisted synthetic jet actuator configured to provide air
flow control at an aerodynamic surface of the aircraft, the aerodynamic structure
having an aerodynamic surface and forming an aperture through the aerodynamic surface,
and the plasma-assisted synthetic jet actuator comprising: one or more walls forming
a chamber within the aerodynamic structure and adjacent to the aerodynamic surface,
wherein the chamber is in fluid communication with an ambient environment through
the aperture; and an ionizing device disposed at the aperture and configured to ionize
one or more chamber gases exiting through the aperture. The plasma-assisted synthetic
jet actuator may also include a gas propulsion device configured to propel one or
more chamber gases through the aperture. The at least one plasma-assisted synthetic
jet actuator may be configured to at least augment one or more control surfaces of
the aircraft. The synthetic jet actuator may also include a first power supply providing
a first signal to the gas propulsion device, and a second power supply providing a
second signal to the ionizing device, wherein the first signal is synchronized with
the second signal.
[0010] The invention can involve a method to improve aerodynamic properties of an aerodynamic
structure that may include providing air flow control at the aerodynamic structure
by ionizing one or more gases exiting through an aperture formed in an aerodynamic
surface of the aerodynamic structure. The the air flow control may be provided by
a plasma-assisted synthetic jet actuator that can include one or more walls forming
a chamber within the aerodynamic structure and adjacent to the aerodynamic surface,
wherein the chamber is in fluid communication with an ambient environment through
the aperture; and an ionizing device disposed at the aperture and configured to ionize
one or more chamber gases exiting through the aperture. The method may also include
propelling one or more chamber gases through the aperture using a gas propulsion device.
[0011] The aerodynamic structure may be included in an aircraft, and wherein the air flow
control is used to at least augment one or more control surfaces of the aircraft.
The aerodynamic structure may be an inlet of a jet engine of the aircraft. The plasma-assisted
synthetic jet actuator may also include a gas propulsion device coupled to a first
power supply, and an ionizing device coupled to a second power supply, wherein a first
signal provided by the first power supply is synchronized with a second signal provided
by the second power supply.
[0012] The features, functions, and advantages that have been discussed may be achieved
independently in various embodiments or may be combined in yet other embodiments,
further details of which can be seen with reference to the following description and
drawings.
BRIEF DESCRIPTION OF ILLUSTRATIONS
[0013] So that the manner in which the above recited features of the present disclosure
can be understood in detail, a more particular description of the disclosure, briefly
summarized above, may be had by reference to embodiments, some of which are illustrated
in the appended drawings. It is to be noted, however, that the appended drawings illustrate
only typical embodiments of this disclosure and are therefore not to be considered
limiting of its scope, for the disclosure may admit to other equally effective embodiments.
Fig. 1 illustrates a cross-section view of an aerodynamic structure in an air flow,
according to embodiments described herein.
Figs. 2A-2C illustrate synthetic jet devices, according to embodiments described herein.
Fig. 3 illustrates a controller for synthetic jet devices, according to embodiments
described herein.
Fig. 4A illustrates an aircraft configured to include synthetic jet devices, according
to embodiments described herein.
Figs. 4B and 4C illustrate configurations for synthetic jet devices in an aerodynamic
structure, according to embodiments described herein.
[0014] To facilitate understanding, identical reference numerals have been used, where possible,
to designate identical elements that are common to the figures. It is contemplated
that elements disclosed in one embodiment may be beneficially utilized on other embodiments
without specific recitation. The illustrations referred to here should not be understood
as being drawn to scale unless specifically noted. Also, the drawings are often simplified
and details or components omitted for clarity of presentation and explanation. The
drawings and discussion serve to explain principles discussed below, where like designations
denote like elements.
DETAILED DESCRIPTION
[0015] To provide enhanced control of air flow at aerodynamic structures, various actuating
devices (described in greater detail below) may be included in or on the aerodynamic
structures. By controlling the propulsion of gases from the chambers of the actuating
devices (
i.e., by controlling volumetric flow rate, direction, etc.), and further by selectively
ionizing propelled gases, better air flow control near the actuating devices may be
achieved. By ionizing the propelled gases, a larger plasma may be formed near the
aerodynamic surfaces, which in turn causes a greater attraction force on the passing
air flow. As a result, aerodynamic structures that include these actuating devices
may exhibit greater aerodynamic performance, such as decreased drag force, increased
flow attachment, reduced noise, and reduced turbulent wake. Consequently, the aerodynamic
structures may be less prone to stalls and may have decreased stall speeds, and may
be able to operate at greater angles of attack without inducing stalls. The propelled,
ionized gases may provide superior performance at supersonic or hypersonic speeds.
[0016] Fig. 1 illustrates a cross-section view of an aerodynamic structure in an air flow,
according to embodiments described herein. For example, aerodynamic structure 100
could represent a device in operation, such as an aircraft wing, a horizontal or vertical
stabilizer of an aircraft, or other surface during flight, or could represent a device
fixed in a wind tunnel and coupled to appropriate instrumentation or in an experimental
configuration. Of course, the aerodynamic structure 100 need not be limited to aerospace
applications, but could represent devices used in numerous other contexts, such as
high-performance automotive or other commercial or personal transportation, wind power
generation, etc. As depicted, aerodynamic structure 100 is disposed within an ambient
environment 115. Ambient environment 115 includes a fluid generally surrounding the
aerodynamic structure 100 such as atmospheric air; of course, the environment may
include other gases or liquids. Aerodynamic structure 100 is shown as an airfoil 110,
though similar principles may certainly be applied to devices having different sizes,
shapes, or configurations. As shown, air flow 130 passes over and under airfoil 110
from left to right. Air flow 130 is generally laminar (
i.e., smooth), but air flow 130 could also include portions of turbulent flow. As the
air flow passes over and under the airfoil, the interaction produces aerodynamic forces
in various directions, such as lift force 112 and drag force 114 components.
[0017] The air flow interaction further creates a boundary layer 120 of air, in which the
air velocity is gradually reduced from a free stream velocity (
i.e., the velocity at points where the aerodynamic structure does not affect the air flow)
to approximately a zero velocity at the surface of the aerodynamic structure 110.
The size and shape of boundary layer 120 is related to the aerodynamic properties
of the structure, as well as the velocity of the air flow; thus, by altering the size
and/or shape of the boundary layer, the amount of drag force created by the structure
may also be changed.
[0018] Figs. 2A-2C illustrate synthetic jet devices, according to embodiments described
herein. Synthetic jet devices 200, 280, 298 may generally be included in an aerodynamic
structure 202 and operated to affect a boundary layer 120, thus providing reduced
drag and other improvements in aerodynamic performance. The effect of the synthetic
jet devices on boundary layer 120 may generally be reflected by a reduction of the
boundary layer height
hBL, either locally (
i.e., proximate to the synthetic jet device), or along at least a portion of the aerodynamic
structure. The synthetic jet devices are further configured to ionize gases propelled
out from a chamber, and may thereby exhibit a greater effect on (and offer better
control of) passing air flow 130. Several elements in Figs. 2A-2C share common reference
numbers; unless indicated otherwise, the elements may operate or behave in the same
or in a substantially similarly manner.
[0019] Synthetic jet device 200 includes one or more walls 205 forming a chamber 210. The
shape and position of the one or more walls may be selected in order to form chamber
210 with a desired shape and/or volume; for example, the walls may have a rounded
shape (from a top view) to form a cylindrical chamber, or the walls may be formed
at right angles to form a rectangular chamber. Of course, walls 205 may have a non-uniform
profile, such as tapered from top to bottom (or vice versa). The volume of chamber
210 may be selected so as to optimize performance characteristics of the synthetic
jet device; the shape of chamber 210 may also be selected to optimize performance,
and may further account for practical considerations (
i.e., limitations associated with placement of the synthetic jet device within aerodynamic
structure 202).
[0020] Synthetic jet device 200 includes a piezoelectric-actuated diaphragm 215, which is
physically coupled to the one or more walls 205 and forms a boundary of chamber 210.
A power supply 220 is coupled to the piezoelectric-actuated diaphragm 215 and configured
to cause the diaphragm to oscillate in an upward and downward motion (as shown by
the adjacent arrows). Of course, the direction and/or frequency of oscillation may
vary depending on the orientation of the diaphragm and/or the synthetic jet device
200. The oscillation of the diaphragm causes pressure changes within chamber 210,
which in turn causes air outside the synthetic jet device 200 to be alternately drawn
into and propelled out of chamber 210 through aperture 225 (the air movement is represented
by arrows 230).
[0021] By controlling the frequency and magnitude of the oscillations of the diaphragm (and
based on the current conditions of air flow 130), the aerodynamic performance of a
particular surface or device may be improved. To provide this control, the power supply
220 may generally be an alternating current (AC) power supply, and may be configured
to generate any feasible signal to provide to the diaphragm, such as a sine wave,
square wave, ramp, sawtooth, etc. The power supply 220 may be further configured to
use pulse-width modulation (PWM) in order to provide a signal having a desired duty
cycle to the diaphragm. Power supply 220 may be disposed within aerodynamic structure202.
[0022] In alternative embodiments, diaphragm 215 may be actuated using different means;
for example, using electrostatic, electromagnetic, hydraulic, or pneumatic means.
In another embodiment, a piston assembly may be used instead of the diaphragm. The
piston assembly may form a seal with walls 205 and provide the desired pressure changes
within chamber 210 to operate the synthetic jet device.
[0023] Synthetic jet device 200 is positioned adjacent to an aerodynamic surface 235, and
may include one or more top walls 240 coupled to the walls 205; the one or more top
walls 240 may form part of aerodynamic surface 235 and may be formed of the same material
as the rest of aerodynamic surface 235, or may alternately be formed of a different
material. If top wall(s) 240 are not included, walls 205 may be coupled directly to
the aerodynamic surface 235, so that aerodynamic surface 235 forms a boundary of chamber
210.
[0024] In an alternative embodiment, the synthetic jet device 200 may be set in from an
aerodynamic surface 235, thereby providing a selected depth or thickness of the material
of the aerodynamic surface between the synthetic jet device 200 and the ambient environment
115.
[0025] In order to affect the air flow 130 moving in ambient environment 115, synthetic
jet device 200 is in fluid communication with ambient environment 115 through an aperture
225 that is formed through aerodynamic surface 235. Additionally or alternately, the
aperture may be formed through the one or more top walls 240 of the synthetic jet
device 200. Aperture 225 may have any desired shape and size, and may be selected
so as to optimize performance characteristics of the synthetic jet device. In one
embodiment, the aperture is circular (as seen from a top view), and may have a fixed
diameter between about ten (10) microns and about one hundred (100) microns. In other
embodiments, the size of the aperture may be mechanically adjustable in order to control
the velocity of fluid flowing therethrough. For example, the aperture could include
a motorized valve coupled to a power supply, an adjustable shutter, and/or a movable
lid assembly disposed adjacent to the aperture.
[0026] Synthetic jet device 200 further includes an ionizing device 250 disposed at the
aperture 225. The ionizing device 250 may comprise any type of device capable of ionizing
air or other gases, which includes devices configured to produce electric or magnetic
fields suitable for ionization. As shown, the ionizing device 250 includes a surface
electrode 255 and an inner electrode 260, and each electrode 255, 260 is coupled to
a power supply 265. The electrodes may have any feasible shape and size, and may be
constructed of any feasible conductive material. In one embodiment, the electrodes
may be constructed of a copper foil. In other embodiments, electrode materials may
be selected for conductive, structural, and/or other properties; example materials
may include graphite, carbon, titanium, brass, silver, platinum, and so forth. To
enable electrodes 255, 260 to generate the desired electric or magnetic fields and
to avoid electrical shorts, aerodynamic surface 235 and/or top wall(s) 240 may be
constructed of a dielectric material (or at least significantly less conductive than
the material selected for electrodes 255, 260). Consistent with generally desirable
aerodynamic properties, some embodiments may provide an aerodynamic surface 235 and/or
top wall(s) 240 that are constructed of carbon fiber, carbon fiber-reinforced polymer,
or other composite materials having a suitable strength-to-weight ratio. Of course,
aerodynamic surface 235 and top wall(s) 240 may be constructed of different materials.
[0027] In several embodiments, each electrode may be attached adjacent to the aerodynamic
surface or to the top wall(s), and may have an opening that corresponds to the size
and position of aperture 225. In one embodiment, each electrode may be ring-shaped,
having a circular opening. The surface electrode 255 may be protected from the conditions
of ambient environment 115 by including an insulating layer 268 configured to at least
partially cover the surface electrode. The material of insulating layer 268 may be
selected based on its thickness or other aerodynamic properties; as insulating layer
268 extends into the ambient environment 115 away from aerodynamic surface 235, too
great a thickness may cause an undesirable change in the aerodynamic properties of
the aerodynamic surface 235 (
e.g., a large thickness tends to create additional drag force). Examples of insulating
layer 268 may include an insulating tape or layer(s) of a film coating or of paint.
The insulating layer material may primarily be selected based on its dielectric properties
(
i.e., its ability to withstand operating voltages at a desired thickness or size), and
may also be selected for its thermal, chemical, or mechanical resistance properties.
In one embodiment, the insulating layer may be a Kapton® (a registered trademark of
E.I. du Pont de Nemours and Company) tape or film; other insulating layer materials
may include polyimides, polyamides, polyamide-imides, polyetheretherketones, or other
polymers having suitable properties.
[0028] In alternate embodiments, the surface electrode may be embedded fully or partially
beneath the aerodynamic surface, thereby reducing (or eliminating) the effects caused
by its profile on the aerodynamic surface. For example, top wall(s) 240 may include
a recess of a suitable size and shape to receive the surface electrode adjacent to
aerodynamic surface 235. To protect the surface electrode from environmental conditions,
the surface electrode could be completely enclosed within the material of top wall(s)
240 or of aerodynamic surface 235, or the size (e.g., depth) of the recess could be
selected to further include an insulating layer 268 beneath the aerodynamic surface,
thus protecting the surface electrode while minimizing any profile on the aerodynamic
surface.
[0029] As shown, insulating layer 268 extends only to the lateral edges of aperture 225.
In other embodiments, however, the size of the opening in electrodes 255, 260 may
vary from the size of the aperture 225; for example, surface electrode 255 may have
an opening that is larger than the aperture 225. In such an embodiment, the insulating
layer 268 may be formed over the entire surface electrode 255, thus fully shielding
the surface electrode 255 from the ambient environment 115 without altering the size
of aperture 225. The electrode opening may have any feasible size, constrained by
an ability to generate the electric or magnetic fields necessary to ionize propelled
gases. Because electrodes 255, 260 are generally aligned with each other (
i.e., having little or no lateral offset), a greater ionization efficiency may be realized
during operation as a larger fraction of electric field lines may be used for ionization.
[0030] Electrodes 255, 260 are coupled to power supply 265, which has parameters (e.g.,
frequency and magnitude) selected that are capable of ionizing gases as they are propelled
out from the synthetic jet device 200 into the ambient environment 115. The ionized,
propelled gases may form a plasma 270 adjacent to or near the synthetic jet device
200, which will generally attract air flow 130 toward the aerodynamic surface 235.
Power supply 265 is generally an alternating current (AC) power supply and similar
to power supply 220 described above, and may be configured to generate any feasible
signal (for example, sine wave, square wave, PWM, etc.) to provide to the electrodes
255, 260 for ionizing the propelled gases.
[0031] In some embodiments, the signals provided to both the piezoelectric-actuated diaphragm
215 and to electrodes 255, 260 may be a common signal. One embodiment may provide
a common signal to both by using a single power supply (as power supply 220 and as
power supply 265). Another embodiment may provide power supplies 220 and 265 as separate
entities, but synchronize their respective outputs so that essentially the same signal
is provided.
[0032] In other embodiments, the signals provided to the piezoelectric-actuated diaphragm
215 and to electrodes 255, 260 may differ, but may be selected to provide improved
performance of the synthetic jet device 200. For example, the signal provided to piezoelectric-actuated
diaphragm 215 may be selected to propel chamber gases at a particular volumetric flow
rate and/or cyclic frequency through the aperture 225. The signal provided to electrodes
255, 260 may be optimally synchronized to the signal provided to piezoelectric-actuated
diaphragm 215; for example, the signal provided to the electrodes may be delayed (
i.e., phase shifted) by a predetermined amount, such that pulses provided at the electrodes
255, 260 are coordinated to ionize a greater amount of air as it is propelled through
the aperture 225. In other words, a volume of air is propelled by a piezoelectric-actuated
diaphragm 215 in response to the signal pulse provided by power supply 220. Instead
of pulsing power supply 265 at the same time as power supply 220, the pulses of power
supply 265 may be selectively delayed to reflect an amount of time required for the
propelled volume to physically reach the aperture 225. And by applying the ionizing
pulses to electrodes 255, 260 as relatively larger amounts of air reaches the aperture
225, a greater ionization efficiency may be achieved (
i.e., more ionization occurs for the amount of power delivered to the synthetic jet device
200).
[0033] Further, in some embodiments, the power supply 265 may be configured to provide ionizing
pulses to electrodes 255, 260 only during a selected portion of the signal cycle that
is provided to the piezoelectric-actuated diaphragm 215. For example, power supply
265 may alter its signal output so as to not ionize gases during periods in which
piezoelectric-actuated diaphragm 215 oscillates in one direction and draws air into
the chamber 210 from the ambient environment 115. During this period, power supply
265 may provide no output signal (
i.e., zero volts) to the electrodes 255, 260, or may instead provide a modified output
signal, perhaps having a lesser amplitude and/or frequency that is calculated not
to ionize any of the gases being drawn into the chamber 210. This may prevent unnecessary
damage or wear to the synthetic jet device caused by forming a plasma inside the chamber
itself, and may further improve ionization efficiency of the synthetic jet device.
[0034] As described above, embodiments may provide power supplies 220 and 265 as separate
power supplies, or as a single power supply. The power supply or supplies may be coupled
to a synchronization module configured to selectively shift or otherwise tune the
signals that are provided to piezoelectric-actuated diaphragm 215 and to electrodes
255, 260. The functions provided by the synchronization module may be achieved through
any feasible means, such as by using hardware components (an application-specific
integrated circuit, or analog circuitry) and/or software.
[0035] Referring now to one embodiment depicted in Fig. 2B, a synthetic jet device 280 is
provided which includes several common components with other embodiments described
above. Synthetic jet device 280 also includes a bottom wall 285 which may be coupled
to the walls 205 in enclosing chamber 210; in one embodiment, bottom wall 285, walls
205, and top wall(s) 240 may be formed as a single unit. A gas source 290 may be in
fluid communication with chamber 210 to provide one or more gases to be propelled
and/or ionized. A flow controller 295 may be disposed between the gas source 290 and
the chamber 210 to control gas flow delivered to the chamber. The gas source may include
one or more gases selected for their ionization capability, such as argon, helium,
etc.
[0036] As the gases provided to chamber 210 approach the ionizing device 250, for example
along a path shown by arrow 297, the ionizing device 250 may ionize the gases in a
manner similar to that described above. The gases may be propelled through chamber
210 toward aperture 225, and ultimately through the aperture, as atoms of the gases
are attracted using the electric or magnetic fields generated by power supply 265
and electrodes 255, 260. In another embodiment, as depicted in Fig. 2C, a synthetic
jet device 298 may use ionizing device 250 to propel atoms of atmospheric air without
a separate gas source.
[0037] Of course, in all the embodiments, a pressure differential may exist between the
chamber 210 and ambient environment 115. For example, the velocity of air flow 130
may cause a decreased air pressure in the ambient environment relative to the pressure
within the chamber. This pressure differential may be beneficially used to supplement
the propulsion provided by the various gas propulsion devices described herein, or
in other embodiments the pressure differential may be used as the sole source of propulsion.
[0038] Embodiments may achieve additional air flow control by permitting synthetic jet devices
200, 280, 298 to be steerable. For example, top wall(s) 240 may be comprised of a
flexible material, such as rubber, and walls 205 or bottom wall 285 may be physically
connected to one or more actuating devices configured to pivot the synthetic jet device
while the physical couplings between the aerodynamic surface 235, walls 205, and the
top wall are maintained. Additionally or alternatively, the walls (
i.e., the top walls, walls, and/or bottom wall) of the synthetic jet devices may be suitably
shaped and/or disposed within the aerodynamic structure to permit steering movement
by the actuating devices. The actuating devices may include one or more electromechanical
or pneumatic devices physically coupled to the synthetic jet device at discrete points
or areas, or coupled to a pivoting surface adjacent to the synthetic jet device (for
example, a generally flat surface coupled beneath bottom wall 285). Of course, different
synthetic jet devices may be steered together or independently.
[0039] Additionally or alternatively, a steering function may be performed using one or
more electromagnets adjacent to or in proximity of the synthetic jet devices, and
for example disposed within the aerodynamic structure and coupled to a power supply.
When appropriate power signals are applied to the electromagnets, the magnetic fields
generated may influence (
i.e., may either attract or repel) the ionized particles exiting the aperture of the synthetic
jet devices, and thereby selectively steer the direction of the output.
[0040] No matter the configuration selected to achieve the steering functions, the opening
of top wall(s) 240 of the steerable synthetic jet device may remain at least partially
aligned with at the aperture in order to allow propelled gases to be ionized and to
exit the chamber.
[0041] By controlling the propulsion of gases out from the chamber 210 (by controlling volumetric
flow rate, direction, etc.), the synthetic jet devices 200, 280, 298 may provide better
air flow control past the aerodynamic surface 235, thus providing improved aerodynamic
properties.
[0042] Generally, the size of a formed plasma 190 will be proportional to its ability to
attract air flow 130; that is, by forming a larger plasma, a greater effect on controlling
the air flow may be realized. Providing propelled gases may tend to support formation
of a larger plasma, which may further attract the air flow 130. As a result, synthetic
jet devices 200, 280, 298 can achieve greater penetration into the boundary layer
(in other words, reduce the boundary layer in which drag forces occur), which results
in decreased drag. Additionally, the attraction of air flow 130 to the aerodynamic
surface 235 may provide better flow attachment to the aerodynamic surface; this generally
makes the aerodynamic structure less prone to stalls and may decrease the stall speed
for the structure. Similarly, the improved flow attachment to the aerodynamic structure
may allow for greater angles of attack without stalling, which may be beneficial for
military aircraft or for other high-performance applications. The synthetic jet devices
200, 280, 298 may be particularly well-suited for use across the range of subsonic,
supersonic, and hypersonic speeds, whereas devices not using propelled, ionized gases
may generally be suitable for use only at subsonic speeds.
[0043] Fig. 3 illustrates a controller for synthetic jet devices, according to embodiments
described herein. Controller 300 may be employed as a part of an aircraft's overall
flight control arrangement. Controller 300 may be employed using separate computing
hardware from a main controller, or the functionality described herein may be incorporated
as part of a main controller. Controller 300 may be used, for example, with the synthetic
jet devices 200, 280, 298 described above. Controller 300 generally includes one or
more computer processors 310, a memory 330, and an input/output (I/O) interface 350.
[0044] Controller 300 may be coupled through I/O interface 350 to one or more sensors 360,
which may generally provide data to the controller, and may be used to complete a
control feedback loop. Sensors 360 may be configured to measure one or more parameters
of the ambient environment, the aerodynamic structure, or the synthetic jet device,
such as various temperatures, flow rate, air speed, humidity, pressure, electric or
magnetic fields, voltage, current, and so forth. Controller 300 may also be configured
to receive user inputs 370 through the I/O interface 350, for example, using an application
programming interface (API). Data received from sensors 360 may be stored in memory
330 as sensor data 335, and the user inputs 370 may be stored as setpoints or performance
metrics 340 generally reflecting a desired operation of the aerodynamic structure.
[0045] Based on sensor data 335 and the setpoints/performance metrics 340, controller 300
may be configured to calculate or to otherwise determine an optimal employment of
the synthetic jet devices. Such an optimization function may include determining which
of the synthetic jet devices to operate, at what levels to operate
(i.e., power signal magnitude, frequency, and/or gas delivered to the synthetic jet devices),
direction(s) to steer the output of synthetic jet devices, and so forth. The optimization
function may occur substantially continuously, or may be performed at intervals by
the processor 310.
[0046] Controller 300 is further configured to provide control signals 380 to several components
of the synthetic jet devices. The control signals 380 may be responsive to the determined
optimal employment of the synthetic jet devices, or may reflect user-entered setpoints
or performance metrics 340. For example, power source signals 382 may be used to optimally
control the output provided by power sources 220, 265. In some embodiments, control
signals may be sent to gas sources (gas source signal 384) or to the flow controller
295; these signals could indicate, among other things, the selection, quantities,
and distribution of gases to be provided to the chamber 210 for propulsion and ionization.
Controller 300 may also be configured to provide steering control signals 388 to one
or more actuators (or electromagnets) configured to alter the direction of propelled
gases from the synthetic jet devices, generally as disclosed above.
[0047] Fig. 4A illustrates an aircraft configured to include synthetic jet devices, according
to embodiments described herein. Generally, synthetic jet devices 200, 280, 298 may
be included in aircraft 400 anywhere that smoother or better controlled air flow is
desired. For example, synthetic jet devices 200, 280, 298 may be provided along the
leading edge and/or trailing edge (or essentially at any other desired position) of
the aircraft's lifting surfaces such as wings 410, and may be used to augment or to
entirely replace traditional control surfaces such as flaps, slats, ailerons, spoilers,
winglets, etc. Embodiments may include synthetic jet devices disposed at approximately
corresponding positions on opposite sides of each wing 410.
[0048] Synthetic jet devices 200, 280, 298 may be provided along the leading edge and/or
trailing edge (or essentially at any other desired position) of horizontal stabilizer
420 or vertical stabilizer 430, and may be used to augment or to entirely replace
traditional control surfaces such as rudders, elevators, etc. Embodiments may include
synthetic jet devices disposed at approximately corresponding positions on opposite
sides of the horizontal stabilizer 420, or on vertical stabilizer 430.
[0049] Synthetic jet devices 200, 280, 298 may also be included at an air inlet of jet engines
440, which are the thrust source for aircraft 400. Smoothing the air flow provided
to the jet engines may result in more stable and/or more efficient operation of the
jet engines, and as described above may permit extended operation of the jet engines
(for example, beyond rated limits at least temporarily).
[0050] Synthetic jet devices 200, 280, 298 may also be included anywhere along the fuselage
450. The synthetic jet devices may be advantageously placed adjacent to or near auxiliary
components of the aircraft that protrude, such as radio antennas, and that generally
decrease the aerodynamic properties of the aircraft (
i.e., create additional drag). For example, one or more synthetic jet devices could be
disposed fore or aft (with respect to the air flow direction) of landing gear 460
to provide smoother air flow past the landing gear when deployed, and thus better
overall aerodynamic properties for the aircraft. The synthetic jets could also be
selectively turned off or not used when the landing gear is retracted, that is, when
compensating for the effects of the landing gear is unnecessary.
[0051] While aircraft 400 is depicted as a commercial airplane, the principles and methods
may be similarly applied to personal aircraft, sport aircraft, military aircraft,
etc. The synthetic jet devices described herein may be included on fixed or moving
surfaces (for example, the rotor blades of a helicopter) while producing similar advantages.
Still further, the principles and methods described herein may also be applied in
other aerodynamic fields, such as high-performance automotive or other commercial
or personal transportation, wind power generation, etc.
[0052] Figs. 4B and 4C illustrate configurations for synthetic jet devices in an aerodynamic
structure, according to embodiments described herein. Assembly 470 includes an aerodynamic
surface 230 and four (4) synthetic jet devices 475 disposed in a single row. Synthetic
jet devices 475 may be the same or may operate in a substantially similar manner to
synthetic jet devices 200, 280, 298 described above. For simplicity, the aerodynamic
surface 235 adjacent to each of the synthetic jet devices 475 is shown having the
same width as the synthetic jet devices; however, the surface may extend such that
the synthetic jet devices are surrounded by the aerodynamic surface. These configurations
are provided only as non-limiting examples; of course, any number of synthetic jet
devices may be used, in any feasible disposition or arrangement, such as an array
having multiple rows and columns, an array having staggered rows or columns, a radial
arrangement, and so forth. Each of the synthetic jet devices includes an aperture
225, through which chamber gases are propelled. In one embodiment, surface electrodes
255 corresponding to each of the synthetic jet devices are included as a single strip
electrode that is shared by multiple synthetic jet devices (in this case, one strip
electrode corresponding to the entire row) and having openings corresponding to the
apertures of each synthetic jet device 475. For ease of display, the strip electrode
is illustrated in an exploded view; normally, the strip electrode is disposed adjacent
to the synthetic jet devices and/or the aerodynamic surface 235. The surface electrode
255 is coupled to power supply 265, which in turn is coupled to an inner electrode
260 (not shown) disposed in each of the synthetic jet devices 475.
[0053] Referring now to the embodiment illustrated in Fig. 4C, assembly 490 includes aerodynamic
surface 235 and two (2) synthetic jet devices 475 disposed in a row. In this embodiment,
a distinct surface electrode 255 is provided to each synthetic jet device 475. While
depicted here as circular electrodes having a circular opening corresponding to size
of aperture 225, the surface electrodes 255 may alternately have any feasible shape
and size, as discussed above. The surface electrodes 255 are each coupled to a power
supply 265, which in turn is coupled to an inner electrode 260 (not shown) disposed
in each of the synthetic jet devices 475. While separate power supplies 265 are shown,
alternate embodiments may provide a single power supply 265 coupled to multiple surface
electrodes 255.
[0054] The descriptions of the various embodiments of the present disclosure have been presented
for purposes of illustration, but are not intended to be exhaustive or limited to
the embodiments disclosed. Many modifications and variations will be apparent to those
of ordinary skill in the art without departing from the scope and spirit of the described
embodiments. The terminology used herein was chosen to best explain the principles
of the embodiments, the practical application or technical improvement over technologies
found in the marketplace, or to enable others of ordinary skill in the art to understand
the embodiments disclosed herein.
[0055] As will be appreciated by one skilled in the art, aspects of the present disclosure
may be embodied as a system, method, or computer program product. Accordingly, aspects
of the present disclosure may take the form of an entirely hardware embodiment, an
entirely software embodiment (including firmware, resident software, micro-code, etc.)
or an embodiment combining software and hardware aspects that may all generally be
referred to herein as a "circuit," "module" or "system." Furthermore, aspects of the
present disclosure may take the form of a computer program product embodied in one
or more computer readable medium(s) having computer readable program code embodied
thereon.
[0056] Any combination of one or more computer readable medium(s) may be utilized. The computer
readable medium may be a computer readable signal medium or a computer readable storage
medium. A computer readable storage medium may be, for example, but not limited to,
an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system,
apparatus, or device, or any suitable combination of the foregoing. More specific
examples (a non-exhaustive list) of the computer readable storage medium would include
the following: an electrical connection having one or more wires, a portable computer
diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an
erasable programmable read-only memory (EPROM or Flash memory), an optical fiber,
a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic
storage device, or any suitable combination of the foregoing. In the context of this
document, a computer readable storage medium may be any tangible medium that can contain,
or store a program for use by or in connection with an instruction execution system,
apparatus, or device.
[0057] A computer readable signal medium may include a propagated data signal with computer
readable program code embodied therein, for example, in baseband or as part of a carrier
wave. Such a propagated signal may take any of a variety of forms, including, but
not limited to, electro-magnetic, optical, or any suitable combination thereof. A
computer readable signal medium may be any computer readable medium that is not a
computer readable storage medium and that can communicate, propagate, or transport
a program for use by or in connection with an instruction execution system, apparatus,
or device.
[0058] Program code embodied on a computer readable medium may be transmitted using any
appropriate medium, including but not limited to wireless, wireline, optical fiber
cable, RF, etc., or any suitable combination of the foregoing.
[0059] Computer program code for carrying out operations for aspects of the present disclosure
may be written in any combination of one or more programming languages, including
an object oriented programming language such as Java, Smalltalk, C++ or the like and
conventional procedural programming languages, such as the "C" programming language
or similar programming languages. The program code may execute entirely on the user's
computer, partly on the user's computer, as a stand-alone software package, partly
on the user's computer and partly on a remote computer or entirely on the remote computer
or server. In the latter scenario, the remote computer may be connected to the user's
computer through any type of network, including a local area network (LAN) or a wide
area network (WAN), or the connection may be made to an external computer (for example,
through the Internet using an Internet Service Provider).
[0060] Aspects of the present disclosure are described above with reference to flowchart
illustrations and/or block diagrams of methods, apparatus (systems) and computer program
products according to embodiments of the disclosure. It will be understood that each
block of the flowchart illustrations and/or block diagrams, and combinations of blocks
in the flowchart illustrations and/or block diagrams, can be implemented by computer
program instructions. These computer program instructions may be provided to a processor
of a general purpose computer, special purpose computer, or other programmable data
processing apparatus to produce a machine, such that the instructions, which execute
via the processor of the computer or other programmable data processing apparatus,
create means for implementing the functions/acts specified in the flowchart and/or
block diagram block or blocks.
[0061] These computer program instructions may also be stored in a computer readable medium
that can direct a computer, other programmable data processing apparatus, or other
devices to function in a particular manner, such that the instructions stored in the
computer readable medium produce an article of manufacture including instructions
which implement the function/act specified in the flowchart and/or block diagram block
or blocks.
[0062] The computer program instructions may also be loaded onto a computer, other programmable
data processing apparatus, or other devices to cause a series of operational steps
to be performed on the computer, other programmable apparatus or other devices to
produce a computer implemented process such that the instructions which execute on
the computer or other programmable apparatus provide processes for implementing the
functions/acts specified in the flowchart and/or block diagram block or blocks.
[0063] The flowchart and block diagrams in the Figures illustrate the architecture, functionality,
and operation of possible implementations of systems, methods, and computer program
products according to various embodiments of the present disclosure. In this regard,
each block in the flowchart or block diagrams may represent a module, segment, or
portion of instructions, which comprises one or more executable instructions for implementing
the specified logical function(s). In some alternative implementations, the functions
noted in the block may occur out of the order noted in the figures. For example, two
blocks shown in succession may, in fact, be executed substantially concurrently, or
the blocks may sometimes be executed in the reverse order, depending upon the functionality
involved. It will also be noted that each block of the block diagrams and/or flowchart
illustration, and combinations of blocks in the block diagrams and/or flowchart illustration,
can be implemented by special purpose hardware-based systems that perform the specified
functions or acts or carry out combinations of special purpose hardware and computer
instructions.
[0064] Further, the invention comprises embodiments according to the following clauses:
Clause 1: A plasma-assisted synthetic jet actuator, comprising:
an aerodynamic structure having an aerodynamic surface and forming an aperture through
the aerodynamic surface;
one or more walls forming a chamber within the aerodynamic structure and adjacent
to the aerodynamic surface, wherein the chamber is in fluid communication with an
ambient environment through the aperture; and
an ionizing device disposed at the aperture and configured to ionize one or more chamber
gases exiting through the aperture.
Clause 2: The plasma-assisted synthetic jet actuator of clause 1, wherein a pressure
differential between the chamber and the ambient environment causes the one or more
chamber gases to exit through the aperture.
Clause 3: The plasma-assisted synthetic jet actuator of clause 1, further comprising
a gas propulsion device configured to propel the one or more chamber gases through
the aperture.
Clause 4: The plasma-assisted synthetic jet actuator of clause 3, wherein the gas
propulsion device is a piezoelectric-actuated diaphragm.
Clause 5: The plasma-assisted synthetic jet actuator of clause 3, wherein the ionizing
device and the gas propulsion device are the same device.
Clause 6: The plasma-assisted synthetic jet actuator of clause 1, wherein the ionizing
device comprises first and second electrodes disposed on opposing sides of the aerodynamic
surface.
Clause 7: The plasma-assisted synthetic jet actuator of clause 6, further comprising
an insulating layer configured to at least partially cover one of the first and second
electrodes.
Clause 8: The plasma-assisted synthetic jet actuator of clause 1, wherein the ionized
chamber gases are steerable using at least one of an actuating device configured to
pivot the plasma-assisted synthetic jet actuator and one or more electromagnets adjacent
to the plasma-assisted synthetic jet actuator.
Clause 9: The plasma-assisted synthetic jet actuator of clause 3, further comprising
a first power supply providing a first signal to the gas propulsion device, and a
second power supply providing a second signal to the ionizing device, wherein the
first signal is synchronized with the second signal.
Clause 10: The plasma-assisted synthetic jet actuator of clause 9, wherein a pulse
of the second signal is delayed by a predetermined amount from a pulse of the first
signal, the predetermined amount based on an amount of time for a volume of the propelled
one or more chamber gases to reach the aperture.
Clause 11: An aircraft, comprising:
a thrust source;
one or more lifting surfaces configured to generate a lift force when coupled to the
thrust source; and
at least one plasma-assisted synthetic jet actuator configured to provide air flow
control at an aerodynamic surface of the aircraft, the aerodynamic structure having
an aerodynamic surface and forming an aperture through the aerodynamic surface, and
the plasma-assisted synthetic jet actuator comprising:
one or more walls forming a chamber within the aerodynamic structure and adjacent
to the aerodynamic surface, wherein the chamber is in fluid communication with an
ambient environment through the aperture; and
an ionizing device disposed at the aperture and configured to ionize one or more chamber
gases exiting through the aperture.
Clause 12: The aircraft of clause 11, wherein the plasma-assisted synthetic jet actuator
further comprises a gas propulsion device configured to propel one or more chamber
gases through the aperture.
Clause 13: The aircraft of clause 11, wherein the at least one plasma-assisted synthetic
jet actuator is configured to at least augment one or more control surfaces of the
aircraft.
Clause 14: The aircraft of clause 12, the synthetic jet actuator further comprising
a first power supply providing a first signal to the gas propulsion device, and a
second power supply providing a second signal to the ionizing device, wherein the
first signal is synchronized with the second signal.
Clause 15: A method to improve aerodynamic properties of an aerodynamic structure,
comprising:
providing air flow control at the aerodynamic structure by ionizing one or more gases
exiting through an aperture formed in an aerodynamic surface of the aerodynamic structure.
Clause 16: The method of clause 15, wherein the air flow control is provided by a
plasma-assisted synthetic jet actuator, comprising:
one or more walls forming a chamber within the aerodynamic structure and adjacent
to the aerodynamic surface, wherein the chamber is in fluid communication with an
ambient environment through the aperture; and
an ionizing device disposed at the aperture and configured to ionize one or more chamber
gases exiting through the aperture.
Clause 17: The method of clause 16, further comprising propelling one or more chamber
gases through the aperture using a gas propulsion device.
Clause 18: The method of clause 15, wherein the aerodynamic structure is included
in an aircraft, and wherein the air flow control is used to at least augment one or
more control surfaces of the aircraft.
Clause 19: The method of clause 18, wherein the aerodynamic structure is an inlet
of a jet engine of the aircraft.
Clause 20: The method of clause 16, the plasma-assisted synthetic jet actuator further
comprising a gas propulsion device coupled to a first power supply, and an ionizing
device coupled to a second power supply, wherein a first signal provided by the first
power supply is synchronized with a second signal provided by the second power supply.
[0065] While the foregoing is directed to embodiments of the present disclosure, other and
further embodiments of the disclosure may be devised without departing from the basic
scope thereof, and the scope thereof is determined by the claims that follow.